Adaptive compensation PWPF modulation method and device of aircraft RCS

A technology of self-adaptive compensation and modulation method, which is applied in the direction of aerospace vehicle guidance devices, aircraft, aerospace vehicles, etc., and can solve the problems of increased fuel consumption of RCS thrusters and high failure rate of RCS thrusters, etc.

Active Publication Date: 2021-02-05
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the existing aircraft RCS thruster (reaction control system, Reaction Control System, RCS), the control accuracy is generally improved by PWPF modulation (PWPF, pulse width pulse frequency), but the existing PWPF modulation is based on frequent thrust On the basis of switching on and off the engine, too frequent switching will increase the fuel consumption of the RCS thruster and lead to a higher failure rate of the RCS thruster

Method used

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  • Adaptive compensation PWPF modulation method and device of aircraft RCS
  • Adaptive compensation PWPF modulation method and device of aircraft RCS
  • Adaptive compensation PWPF modulation method and device of aircraft RCS

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Embodiment 1

[0052] figure 1 It is a flow chart of an adaptive compensation PWPF modulation method for an aircraft RCS provided in Embodiment 1 of the present invention, and the method includes the following steps:

[0053] Step S11: Receive the control torque signal, use the control torque signal to calculate the adaptive damping coefficient algorithm to obtain the damping coefficient, and use the damping coefficient as the coefficient of the damping link of the negative feedback loop of the pulse width pulse frequency modulation.

[0054] In the embodiment of the present invention, the reaction control system (ReactionControl System, RCS) of the existing hypersonic vehicle often uses a constant value thruster, which needs to rely on PWPF modulation (Pulse-Width Pulse-Frequency, PWPF, pulse width pulse frequency modulation) This means to change the real-time control torque required for attitude control into the "digital" variable thrust of the RCS thruster.

[0055] In the embodiment of...

Embodiment 2

[0077] Figure 5 It is a graph of time and switching times of an adaptive compensation PWPF modulation provided by Embodiment 2 of the present invention.

[0078] Figure 5 The four curves in are the added damping coefficients K 11 , K 12 , K 13 as well as K 14 After the PWPF modulation time vs. switching times curve, the damping coefficient K 11 , K 12 as well as K 13 It is the ratio of the input control torque signal to the RCS rated torque E Do the calculation to get, K 14 It is a fixed value of 0.7. in, K 11 , K 12 as well as K 13 The calculation formulas are:

[0079] ;

[0080] ;

[0081] ;

[0082] In the formula, K 11 , K 12 as well as K 13 is the damping coefficient, E is the ratio of the control torque signal to the RCS rated torque.

[0083] In the embodiment of the present invention, K 11 It can be used as the optimal adaptive damping coefficient, so that the switching times of the adaptive compensation PWPF modulation are l...

Embodiment 3

[0087] Figure 7 It is a schematic structural diagram of an adaptive compensation PWPF modulation device for an aircraft RCS provided in Embodiment 3 of the present invention.

[0088] The adaptive compensation PWPF modulation device 700 of the aircraft RCS includes:

[0089] The damping coefficient calculation module 710 is used to receive the control torque signal, use the control torque signal to calculate the damping coefficient through the adaptive damping coefficient algorithm, and use the damping coefficient as the damping link of the negative feedback loop of the pulse width pulse frequency modulation coefficient;

[0090] The torque signal modulation module 720 is configured to use the control torque signal to perform pulse width pulse frequency modulation to obtain a modulated torque signal, and the negative feedback signal in the pulse width pulse frequency modulation uses the damping coefficient and the modulated torque signal Obtained by multiplication.

[0091...

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PUM

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Abstract

The invention provides an adaptive compensation PWPF modulation method and device for an aircraft RCS, and the method comprises the steps: receiving a control moment signal, obtaining a damping coefficient through the operation of an adaptive damping coefficient algorithm through the control moment signal, and taking the damping coefficient as a coefficient of a damping link of a negative feedbackloop of pulse width pulse frequency modulation; performing pulse width pulse frequency modulation by using the control torque signal to obtain a modulated torque signal, and performing multiplicationoperation on a negative feedback signal in pulse width pulse frequency modulation and the modulated torque signal by using the damping coefficient to obtain a negative feedback signal in pulse widthpulse frequency modulation. According to the self-adaptive compensation PWPF modulation method of the aircraft RCS, the PWPF modulation period can be prolonged, the pulse width can be increased, the error reduction capability of each modulation is enhanced, and the total PWPF modulation period number is reduced, so that the total RCS thruster startup and shutdown frequency is reduced, and the fuelconsumption and the failure rate of the RCS thruster are reduced.

Description

technical field [0001] The present invention relates to the field of reaction force control, in particular to an aircraft RCS adaptive compensation PWPF modulation method, device, computer equipment and readable storage medium. Background technique [0002] In the existing aircraft RCS thruster (reaction control system, Reaction Control System, RCS), the control accuracy is generally improved by PWPF modulation (PWPF, pulse width pulse frequency), but the existing PWPF modulation is based on frequent thrust Based on the switch of the engine, too frequent switching will increase the fuel consumption of the RCS thruster and lead to a higher failure rate of the RCS thruster. Contents of the invention [0003] In view of the above problems, the present invention provides an aircraft RCS adaptive compensation PWPF modulation method, device, computer equipment and readable storage medium to reduce fuel consumption and failure rate of RCS thrusters. [0004] In order to achieve ...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/28
CPCB64G1/24B64G1/28B64G1/245
Inventor 宋佳赵鸣飞张严雪徐小蔚罗雨歇
Owner BEIHANG UNIV
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